Multi-loop patrolling configuration method for high-orbit satellite regional protection

Abstract

The application discloses a multi-loop patrolling configuration method for high-orbit satellite regional defense, and comprises the following steps: inputting the number n of defense objects, the initial orbit phase distribution r, the safe guard distance Ar, the first-layer patrolling satellite number m1 and the patrolling loop number p in high-orbit satellite regional defense according to a defense task G and the safe guard distance Ar H ; calculating the orbit height and the phase distribution range of the defense region corresponding to each patrolling loop, the number of satellites on the eastward and westward drifting orbits of the patrolling loop, and the initial phase of the patrolling satellites on the eastward and westward drifting orbits of the patrolling loop; calculating the two impulse velocity increments of the eastward rising and westward descending processes of the patrolling loop, and the orbit transfer time of the eastward rising and westward descending processes; calculating the eastward and westward orbit transfer time corresponding to each patrolling loop, and the fuel consumption of each patrolling satellite in one loop on the patrolling loop according to the initial phase of the patrolling satellites on the eastward and westward drifting orbits of the patrolling loop; and establishing the multi-loop patrolling configuration of the high-orbit satellite regional defense according to the obtained parameters.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a multi-ring patrol configuration method for regional protection of high-orbit satellites. BACKGROUND

[0002] GEO orbit (Geostationary Orbit) has special orbital resource advantages, so major space powers in the world have deployed many high-value strategic satellites such as communication, data relay, electronic reconnaissance, and navigation on the GEO orbit.

[0003] Some countries have made the region with concentrated GEO orbit space resources and assets as the space traffic line and strategic location for key defense. Ten years ago, some countries implemented a number of high-orbit space situation awareness projects in order to ensure their advantages in the field of aerospace, and launched a series of high-orbit reconnaissance satellites based on this, establishing a satellite detection system combining space and ground, including 2 MiTEx satellites, 4 GSSAP satellites, EAGLE aircraft and 3 100kg-level sub-satellites carried by it. These satellites can not only obtain information and data of target spacecraft through various technical means, but also have the ability to carry out rendezvous and close-in operations on other GEO spacecraft, which has posed a certain threat to the space safety of other countries. The situation of space attack and defense game based on space has formed and will continue.

[0004] Therefore, relevant researches on space attack and defense technology have been carried out at home and abroad, mainly focusing on space interception, on-orbit capture, and space reconnaissance. However, these researches are mostly of the offensive type, and in fact, high-value satellites in GEO orbit do not have the ability to play space games, so what is needed is protection technology for these high-value satellites. However, there are few researches on protection patrol configuration design, and most of them are researches on companion configuration design for single spacecraft, while research on patrol configuration design for orbit regions containing multiple high-orbit satellites is still blank. In addition, the fuel resources of high-orbit satellites are very valuable, and the patrol task needs to be executed for a long time, and considering the east and west drift phenomenon in orbit motion, which is a relative motion phenomenon between satellites with different orbit altitudes, and the east and west drift phenomenon is a natural transfer process of the orbit and does not need additional control, which can save fuel while achieving regional protection effect. Therefore, the present application proposes a multi-ring patrol configuration design method for regional protection of high-orbit satellites based on the east and west drift phenomenon. SUMMARY

[0005] In view of the problems in the prior art, the track satellite itself is not provided with the space game capability, and therefore, for the protection technology of the high-value satellite, the application provides a multi-ring patrol configuration method for high-orbit satellite regional protection; the patrol cycle and fuel consumption of the multi-ring patrol configuration are analyzed by the application, and a method capable of saving fuel, being efficient and fast and being capable of long-time execution is provided for the high-orbit regional protection.

[0006] The application is realized by the following technical scheme:

[0007] A multi-ring patrol configuration method for high-orbit satellite regional protection, the configuration method comprises the following steps:

[0008] S1: according to the protection task, inputting the number n of protection objects in the high-orbit satellite regional protection, the initial phase distribution r of the orbit G and the safe escort distance Δr H , the number m1 of first-layer patrol satellites, and the number p of patrol ring layers;

[0009] S2: according to the number p of patrol ring layers, the safe escort distance Δr H , the number m1 of first-layer patrol satellites, calculating the orbit height and phase distribution range of the protection region corresponding to each patrol ring layer, the number of satellites on the eastward and westward orbit of the patrol ring, and the initial phase of the patrol satellite on the eastward and westward orbit of the patrol ring;

[0010] S3: according to the safe escort distance Δr H , calculating the escort distance of the i-th patrol layer , the two pulse velocity increments of the eastward and westward rising process of the patrol ring, and the orbit transfer time of the eastward and westward rising process;

[0011] S4: according to the calculated initial phase of the patrol satellite on the eastward and westward orbit of the patrol ring, calculating the eastward and westward orbit transfer time corresponding to each patrol ring layer, and the fuel consumption of each patrol satellite on the patrol ring per orbit;

[0012] S5: establishing the multi-ring patrol configuration for the high-orbit satellite regional protection according to the obtained parameters.

[0013] Further, the S1 comprises the following steps:

[0014] According to the number n of protection objects, the orbit phase distribution the safe escort distance Δr H , and the number p of patrol ring layers, a geocentric polar coordinate system is established, wherein r i G represents the radial coordinate of the i-th protection object in the polar coordinate, represents the angular coordinate of the i-th protection object in the polar coordinate, i=1,2…n;

[0015] Write n guard objects in the polar coordinate system of the earth's center

[0016] According to the high orbit guard object distribution in the same radius orbit phase distribution r G On the orbit, so the formula is

[0017] Further, S2.1: number the patrol ring from inside to outside, the innermost layer is the first layer, and the outermost layer is the pth layer;

[0018] S2.2: according to the safety escort distance Δr H The escort distance of the ith patrol layer is determined as

[0019] S2.3: according to the escort distance of the ith layer Calculate the guard area range; the phase range of the ith guard area in the polar coordinate system of the earth's center The orbital radius range of the ith guard area in the polar coordinate system of the earth's center

[0020] Where, the initial phase of the patrol satellite on the eastward drifting orbit of the ith patrol ring The initial phase of the patrol satellite on the westward drifting orbit of the ith patrol ring The semi-major axis of the westward drifting orbit of the ith patrol ring And the semi-major axis of the eastward drifting orbit of the ith patrol ring

[0021] Further, the S3 includes the following steps:

[0022] According to the number of first layer patrol satellites m1, the number of patrol satellites on the eastward and westward orbits of each patrol ring is calculated;

[0023] With the increase of each patrol ring by 1 layer, the number of patrol satellites of this layer also increases by 1, and the number of satellites on the ith patrol ring m i is obtained:

[0024] m i = m1+i-1 (24)

[0025] According to the number of patrol satellites m i on the ith patrol ring and the patrol area phase range , the initial configuration design is carried out, and p i and q i patrol satellites are evenly distributed in phase on the eastward and westward orbits of the ith patrol ring, respectively, wherein:

[0026]

[0027]

[0028] The number p of satellites drifting eastward and westward in the i-th layer of the circumferential ring was calculated. i and q i ; where m i =p i +q i ;

[0029] Calculate p on the i-th layer of the eastward drifting orbit. i The initial polar coordinates of the rover satellite are

[0030] The initial polar coordinates of the l-th rover in the i-th layer of the westward drifting orbit are:

[0031] Calculate the initial phase of the roving satellite in the eastward drift orbit of the i-th roving ring, assuming a uniform phase angle distribution. for:

[0032]

[0033] The initial phase of the roving satellite in the westward drift orbit of the i-th roving ring was calculated. for:

[0034]

[0035] Where 'l' represents the l-th rover in the eastward orbit.

[0036] Furthermore, based on the semi-major axis of the i-th layer of the circum-west drifting orbit... and the semi-major axis of the i-th layer of the circum-east drifting orbit The semi-major axis a of the Hohmann transition of the i-th layer inspection ring i Calculations were performed, and the Earth-centered gravitational constant μ was used to determine the velocity increments of the two pulses during the eastward ascent of the i-th layer of the circumpolar ring. Perform calculations;

[0037]

[0038]

[0039] In the formula, μ = 3.986 × 10 14 m 3 s -2 =3.986×10 5 km 3 s -2G represents the gravitational constant of celestial bodies with the earth as the center;

[0040] Similarly, the two pulse velocity increments of the i-th layer of the westward process of the patrol ring The calculation result is:

[0041]

[0042]

[0043] Further, the orbit transfer time of the i-th layer of the westward and eastward process of the patrol ring is calculated

[0044]

[0045] Further, the longitude change of the i-th layer of the eastward and westward process of the patrol ring is determined according to the phase;

[0046] According to the eastward process being from the westward end point to the eastward starting point During the period, the orbit radius does not change,

[0047] The phase angle change is determined as:

[0048]

[0049] The phase angle change of the i-th layer of the westward process of the patrol ring is:

[0050]

[0051] Further, the orbit angular velocities of the i-th layer of the eastward and westward process of the patrol ring and the protective object are calculated respectively according to the orbit height of the three:

[0052]

[0053]

[0054]

[0055] The relative angular velocities of the i-th layer of the eastward and westward process of the patrol satellite relative to the protective object are calculated respectively

[0056]

[0057]

[0058] The transfer time of the eastward drift and the westward drift of the i-th layer of the patrol ring is calculated according to the phase angle range of the eastward drift and the westward drift of the i-th layer of the patrol ring and the relative angular velocity of the eastward drift and the westward drift of the patrol satellite relative to the protected object

[0059]

[0060]

[0061] Further, the patrol cycle T of the i-th layer of the patrol ring is calculated according to the transfer time of the eastward ascent and the westward descent of the i-th layer of the patrol ring and the transfer time of the eastward drift and the westward drift of the i-th layer of the patrol ring i c is:

[0062]

[0063] And the fuel consumption of each patrol satellite of the i-th layer of the patrol ring for one circle can be calculated according to the speed increment of the Hohmann transfer of the i-th layer of the patrol ring

[0064]

[0065] Compared with the prior art, the present application has the following beneficial technical effects:

[0066] The present application provides a multi-ring patrol configuration design method for high-orbit area protection based on the natural transfer phenomenon of the eastward drift and the westward drift in the relative kinematics of the orbit and the Hohmann transfer process, and analyzes the patrol cycle and the fuel consumption of the designed multi-ring patrol configuration. The present application provides a multi-ring patrol configuration design method for high-orbit area protection, which is fuel-saving and efficient and fast.

[0067] The present application provides the initial distribution phase of the patrol satellite on the patrol configuration and the patrol cycle and the long-term fuel consumption of the configuration, and can efficiently and comprehensively complete the multi-ring patrol configuration design and analysis work for the high-orbit satellite area protection, thereby providing a reference for the design of the multi-ring patrol configuration for the high-orbit satellite area protection in the actual engineering application. DETAILED DESCRIPTION

[0068] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced. Obviously, the drawings in the following description only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creating labor.

[0069] Figure 1 A flow chart of a multi-ring patrol configuration method for high-orbit satellite area protection provided by the present application;​

[0070] Figure 2 A phase diagram of a multi-loop patrol configuration method for high-orbit satellite regional protection provided by the embodiment of the present application;

[0071] Figure 3 A guard schematic diagram of a multi-loop patrol configuration method for high-orbit satellite regional protection provided by the embodiment of the present application;

[0072] Figure 4 A Hohmann transfer process schematic diagram of a multi-loop patrol configuration method for high-orbit satellite regional protection provided by the embodiment of the present application;

[0073] Figure 5 A multi-loop distribution schematic diagram of a multi-loop patrol configuration method for high-orbit satellite regional protection provided by the embodiment of the present application;

[0074] Figure 6 A i-layer patrol loop guard region schematic diagram of a multi-loop patrol configuration method for high-orbit satellite regional protection provided by the embodiment of the present application;

[0075] Figure 7 A flow chart of a multi-loop patrol configuration method for high-orbit satellite regional protection provided by the embodiment of the present application. DETAILED DESCRIPTION

[0076] In the following, only certain exemplary embodiments are simply described. As those skilled in the art can recognize, the described embodiments can be modified in various different ways without departing from the spirit or scope of the present application. Therefore, the drawings and the description are considered to be exemplary in nature rather than limiting.

[0077] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0078] Embodiment 1:

[0079] S1: The number of patrol satellites on the eastward and westward orbits of each patrol loop is determined according to the patrol loop layer number p (i = 1, 2, …, p) and the guard distance of the i-layer patrol layer, which is Determination of the safe guard distance of the i-layer patrol layer According to the safe guard distance of the i-layer patrol layer Determination of the protection region range;

[0080] S2: According to the safe guard distance of the i-layer patrol layer And the orbit phase distribution r G Calculation, to obtain the phase range of the i-layer protection region in the geocentric polar coordinate system The phase range of the i-layer protection region in the geocentric polar coordinate system The orbit radius range of the i-th layer protection area in the geocentric polar coordinate system The semi-major axis of the i-th layer patrol ring west drift The semi-major axis of the i-th layer patrol ring east drift

[0081] S3: According to the number of first layer patrol satellites m1, the number of satellites m on the i-th layer patrol ring is calculated i ; The number of patrol satellites on the east drift and west drift orbits of each layer patrol ring; The number of satellites on the east drift orbit of the i-th layer patrol ring is p i And the number of satellites on the west drift orbit of the i-th layer patrol ring is q i , the p i th patrol satellite on the east drift orbit of the i-th layer patrol ring has initial polar coordinates

[0082] The initial phase of the patrol satellite on the east drift orbit of the i-th layer patrol ring and the initial phase of the patrol satellite on the west drift orbit of the i-th layer patrol ring are calculated

[0083] S4: The safety guard distance of the i-th layer patrol layer The semi-major axis a of the i-th layer patrol ring Hohmann transfer is calculated i , and the semi-major axis a of the i-th layer patrol ring Hohmann transfer i , the celestial body gravitational constant μ with the Earth as the center, and the semi-major axis of the i-th layer patrol ring west drift The semi-major axis of the i-th layer patrol ring east drift are calculated, and the two impulse velocity increments of the i-th layer patrol ring east rise process are obtained respectively And according to the given celestial body gravitational constant μ with the Earth as the center, the orbit radius range of the i-th layer protection area in the geocentric polar coordinate system And the semi-major axis a of the i-th layer patrol ring Hohmann transfer i ;

[0084] The two impulse velocity increments of the i-th layer patrol ring east rise process are calculated And the two impulse velocity increments of the i-th layer patrol ring west descent process are calculated And the orbit transfer time t of the west descent process WD , and the orbit transfer time t of the east rise process EU ;

[0085] S5: According to the west descent endpoint The east rise starting point The phase angle change of the i-th layer east drift process is calculated And the phase angle change of the i-th layer west drift process of the patrol ring is calculated The relative angular velocity of the eastward and westward drift of the i-th orbiting ring relative to the protected object, and the transfer time of the eastward and westward drift of the i-th orbiting ring

[0086] S6: The eastward and westward transfer time of the i-th orbiting ring is calculated according to the eastward and westward transfer time of the i-th orbiting ring obtained in step S4 and the eastward and westward transfer time of the i-th orbiting ring obtained in step S5 The orbiting period T of the i-th orbiting ring is calculated i c The fuel consumption of each orbiting satellite on the i-th orbiting ring can be calculated according to the Hohmann transfer speed increment of the i-th orbiting ring obtained in step S3.

[0087] Embodiment 1:

[0088] S1, input the number n of protected objects, the orbit phase distribution, and the safety escort distance Δr in the high-orbit satellite regional protection H , the number m1 of first orbiting satellites, and the number p of orbiting rings;

[0089] S2, determine the orbit height and phase range of the corresponding protection area of each orbiting ring;

[0090] S3, determine the number and phase distribution of the orbiting satellites on each orbiting ring

[0091] S4, calculate the eastward and westward transfer time and the impulse speed increment of each orbiting ring according to the Hohmann transfer process;

[0092] S5, calculate the eastward and westward orbit transfer time of each orbiting ring according to the relative orbit angular velocity;

[0093] S6, calculate and analyze the orbiting period and long-term fuel consumption of each orbiting ring;

[0094] The specific steps of step S1 are as follows:

[0095] The input parameters of the multi-orbiting configuration design method for high-orbit satellite regional protection are the number n of protected objects, the orbit phase distribution where i=1, 2…n, the safety escort distance Δr H and the number p of orbiting rings, as shown in the following equation: Figure 4

[0096] The polar point of the polar coordinate system is the center of the Earth, and the numbering of the protected objects is from west to east, with the westernmost end numbered 1 and the easternmost end numbered n. The direction of the connection line between the center of the Earth and the first protected object is defined as the polar axis, and the polar axis rotates with the first protected object. The positive direction of the angle is clockwise. ​

[0097] Then the n guard objects in the polar coordinate system can be written as:

[0098]

[0099] Since the high-orbit guard objects are distributed on the same radius r G , the formula is

[0100] In the step S2, the orbit height and phase range of the guard area corresponding to each layer of the patrol ring are determined, and the step is described in more detail as follows:

[0101] As shown in Figure 5 the patrol configuration is composed of p layers of patrol rings, the patrol areas of the patrol rings are not the same, the patrol rings are numbered from inside to outside, the innermost layer is the first layer, and the outermost layer is the pth layer,

[0102] According to the safety guard distance Δr H , the guard distance of the ith layer of the patrol layer is determined as where i = 1, 2,..., p.

[0103] Then, according to the guard distance of the ith layer , the guard area range is calculated,

[0104] As shown in Figure 6 , first, the phase range of the ith layer of the guard area in the polar coordinate system is

[0105]

[0106]

[0107]

[0108] Then the orbit radius range of the ith layer of the guard area in the polar coordinate system can be calculated as

[0109]

[0110]

[0111] In the step S3, the number of patrol satellites on each layer of the patrol ring and the initial phase distribution are determined:

[0112] The patrol area of the patrol ring increases with the increase of the layer number, therefore, in order to ensure the patrol effect, the number of patrol satellites on the patrol ring increases by one with each layer, that is, the number of satellites m i on the ith layer of the patrol ring:

[0113] m i = m1 + i - 1 (51)

[0114] Based on the number of inspection satellites m on the i-th layer inspection ring i and the phase range of the inspection area carry out the initial configuration design, and evenly distribute p i satellites and q i satellites on the east-drifting and west-drifting orbits in the i-th layer inspection ring according to the phase respectively, that is, m i = p i + q i , where:

[0115]

[0116]

[0117] The initial polar coordinates of the p i satellites on the east-drifting orbit in the i-th layer inspection ring are where l represents the l-th inspection satellite from west to east on the east-drifting orbit. Similarly, the initial polar coordinates of the l-th inspection satellite from west to east on the west-drifting orbit in the i-th layer inspection ring are

[0118] Then, according to the uniform distribution of the phase angle, the phase angle [[ID=​​​​​​​​​​​​​​​​​​​​​​​​​​On the circular orbit. Therefore, the transfer time and corresponding pulse velocity increment of the westward and eastward drifting processes of the i-th layer of the inspection ring are calculated according to the Hohmann transfer formula. The semi-major axes of the westward and eastward drifting circular orbits of the i-th layer of the inspection ring are respectively Then the semi-major axis a of the Hohmann transition of the i-th layer inspection ring i for:

[0124]

[0125] The two pulse velocity increments during the circum-rising process of the i-th layer. The following can be calculated separately:

[0126]

[0127]

[0128] In the formula, μ = 3.986 × 10 14 m 3 s -2 =3.986×10 5 km 3 s -2 , representing the gravitational constant of a celestial body centered on the Earth.

[0129] Similarly, the velocity increments of the two pulses during the westward descent process of the i-th layer of the inspection ring can be calculated as follows:

[0130]

[0131]

[0132] Next, the orbital transfer time of the westward descent and eastward ascent of the i-th layer of the roving ring is calculated.

[0133]

[0134] The specific process of step S5 is as follows:

[0135] First, determine the longitude changes during the eastward and westward drifting processes of the i-th layer of the inspection loop, such as... Figure 6 As shown, the eastward drifting process originates from the westward descent endpoint. Arrive at the starting point of Dongsheng orbital radius during period No change, phase angle change for:

[0136]

[0137] Similarly, the phase angle change of the westward drift process of the i-th layer can be obtained. for:

[0138]

[0139] The orbit angular velocity of the east drift, the west drift and the protective object of the i-th layer patrol ring is calculated respectively according to the orbit height of the protective object in the east drift, the west drift and the protective object of the i-th layer patrol ring:

[0140]

[0141]

[0142]

[0143] The relative angular velocity of the east drift, the west drift of the patrol satellite relative to the protective object in the east drift, the west drift of the i-th layer patrol ring is calculated respectively

[0144]

[0145]

[0146] The transfer time of the east drift, the west drift of the i-th layer patrol ring is calculated respectively according to the phase angle range of the east drift, the west drift of the i-th layer patrol ring and the relative angular velocity of the east drift, the west drift of the patrol satellite relative to the protective object

[0147]

[0148]

[0149] In step S6, the patrol period and the long-term fuel consumption of each layer patrol ring are calculated and analyzed, and the specific steps include the following steps:

[0150] According to the east rising, west descending transfer time of the i-th layer patrol ring obtained in step S4 And the east drift, west drift transfer time of the i-th layer patrol ring obtained in step S5 The patrol period T of the i-th layer patrol ring is calculated i c is:

[0151]

[0152] The east drift and the west drift in the patrol process are natural transfer processes and do not consume fuel, so the fuel consumption only occurs in the east rising, west descending process. According to the Hohmann transfer speed increment of the i-th layer patrol ring obtained in step S3, the fuel consumption of each patrol satellite single circle on the i-th layer patrol ring can be calculated as:

[0153]

[0154] Example 3:

[0155] In this embodiment, a specific task requirement of implementing patrol protection for 13 satellites distributed on high orbits with a radius of 42164 km is provided, the safe guard distance is 100 km, the initial phase distribution of the target satellites is in the range of 75°E to 135°E longitude, the number of the first layer of patrol satellites is 6, and the number of patrol ring layers is 4. The process of designing a multi-ring patrol configuration for high-orbit satellite regional protection using the method of the application will be listed next.

[0156] The specific steps are as follows:

[0157] Determine the orbit radius, the number of guard satellites, the safe guard distance, the initial phase of the satellites, the number of patrol ring layers, and the number of the first layer of patrol satellites.

[0158] S1, input the number of protected objects n, the orbit phase distribution, and the safe guard distance Δr in high-orbit satellite regional protection. H , the number of the first layer of patrol satellites m1, and the number of patrol ring layers p.

[0159] According to the input, the number of protected objects n is 13, the safe guard distance Δr H is 100 km, the number of the first layer of patrol satellites m1 is 6, the number of patrol ring layers p is 4, and the initial orbit phase distribution is in the range of 75°E to 135°E longitude on the orbit with r G = 42164 km. The protected objects are numbered from west to east according to the phase distribution of the high-orbit satellite protected objects, the westernmost end is numbered 1, and the easternmost end is numbered 13. The polar coordinate system is established with the center of the earth as the polar point and the center of the earth and the line connecting the 1st protected object as the polar axis. The clockwise direction is defined as positive. Then the coordinates of the 13 protected objects in the polar coordinate system are written as:

[0160] (42164, 0°), (42164, 5°), (42164, 10°), …, (42164, 60°) (1)

[0161] S2, determine the orbit height and phase range of the guard region corresponding to each patrol ring.

[0162] The patrol configuration is composed of p = 4 patrol rings. The patrol regions of each patrol ring are not the same, and the patrol rings are numbered from inside to outside,

[0163] According to the safe guard distance Δr H , the guard distance of the i-th patrol layer is determined as where i = 1, 2, …, p. Then, according to the guard distance of the i-th layer, the guard region range is calculated,

[0164] For example,Figure 6 The phase range of the i-th guard zone in the geocentric polar coordinate system is first calculated

[0165]

[0166]

[0167]

[0168] The orbital radius range of the i-th guard zone in the geocentric polar coordinate system can then be calculated

[0169]

[0170]

[0171] S3, determine the number of patrol satellites on each patrol ring and the initial phase distribution;

[0172] The number of patrol satellites on the first patrol ring is m1=6, and the number of patrol satellites on the i-th patrol ring can be calculated as i :

[0173]

[0174] According to equations (9) and (10), the number of patrol satellites on the eastward drifting orbit and the westward drifting orbit of each patrol ring can be calculated as

[0175]

[0176] The initial polar coordinates of the p-th patrol satellite on the eastward drifting orbit of the i-th patrol ring are i wherein,

[0177] l represents the l-th patrol satellite on the eastward drifting orbit from west to east, and the initial phase of the patrol satellite on the eastward drifting orbit of the i-th patrol ring can be calculated according to equation (11):

[0178]

[0179] Similarly, the initial phase of the patrol satellite on the westward drifting orbit of the i-th patrol ring can be calculated according to equation (12)

[0180]

[0181] S4, calculate the corresponding eastward ascending, westward descending transfer time and pulse velocity increment in each patrol ring according to the Hohmann transfer process:

[0182] ​The semi-major axes of the i-th layer's patrol loops around the west and east drifting orbits are respectively... Then the semi-major axis a of the Hohmann transition of the i-th layer inspection ring i For: Among them,

[0183]

[0184] The gravitational constant μ of a celestial body centered on Earth is given as:

[0185] μ=3.986×10 14 m 3 s -2 =3.986×10 5 km 3 s -2 (10)

[0186] The two pulse velocity increments during the circum-rising process of the i-th layer. They are respectively:

[0187]

[0188]

[0189] Similarly, the velocity increments of the two pulses during the westward descent process of the i-th layer inspection ring can be calculated as follows:

[0190]

[0191]

[0192] Next, the orbital transfer time t during the westward descent and eastward ascent processes is calculated. WD t EU

[0193]

[0194] Step 5: Calculate the eastward and westward orbital transfer times for each patrol loop based on the relative orbital angular velocity.

[0195] First, determine the longitude changes during the eastward and westward drifting processes of the i-th layer of the inspection loop. The eastward drifting process originates from the westward descent endpoint. Arrive at the starting point of Dongsheng orbital radius during period No change, phase angle change for:

[0196]

[0197] Similarly, the phase angle change of the westward drift process of the i-th layer can be obtained. for:

[0198]

[0199] The orbital angular velocity of the east drift, west drift and the protective object of the i-th layer of the patrol ring is calculated respectively according to the orbital height of the three:

[0200]

[0201]

[0202]

[0203] The relative angular velocity of the east drift and the west drift of the i-th layer of the patrol ring relative to the protective object is calculated respectively during the east drift and the west drift of the patrol satellite

[0204]

[0205]

[0206] The transfer time of the east drift and the west drift of the i-th layer of the patrol ring is calculated respectively according to the phase angle range of the east drift and the west drift of the i-th layer of the patrol ring and the relative angular velocity of the east drift and the west drift of the patrol satellite relative to the protective object

[0207]

[0208]

[0209] Step 6: Calculate and analyze the patrol period and long-term fuel consumption of each layer of the patrol ring:

[0210] According to the east drift and west drift transfer time of the i-th layer of the patrol ring obtained in step S4 And the east drift and west drift transfer time of the i-th layer of the patrol ring obtained in step S5 The patrol period T of the i-th layer of the patrol ring is calculated i c is:

[0211]

[0212] The east drift and west drift processes in the patrol process are natural transfer processes and do not consume fuel, so fuel consumption only occurs in the east rise and west descent processes. According to the Hohmann transfer speed increment of the i-th layer of the patrol ring obtained in step S3, the fuel consumption of each patrol satellite on the i-th layer of the patrol ring per revolution can be calculated as:

[0213]

[0214] The foregoing merely illustrates the principles of the application and application of its leading features. This application is not limited to the exact details shown above and described herein, and obvious modifications will occur to those skilled in the art upon reading the foregoing description. Thus, it is contemplated to cover any and all modifications falling within the scope of the claims appended hereto. Any recitation of numerical ranges by endpoints is intended to include all values falling within these ranges, along with the endpoints (unless the context clearly dictates otherwise). Any reference to a patent, patent application, or patent publication is intended to refer to that patent, patent application, or patent publication as published, and is not intended to be prior art to the present application.

[0215] Furthermore, it should be understood that although the description above is based on embodiments, not every embodiment contains only one independent technical solution, and the description above is only for the sake of clarity, and those skilled in the art should understand the description as a whole, and the technical solutions in each embodiment can be appropriately combined to form other embodiments that those skilled in the art can understand. The above is only to illustrate the technical idea of the present application, and cannot limit the protection scope of the present application. Any modification made on the basis of the technical idea of the present application and technical solutions falls within the protection scope of the claims of the present application.

Claims

1. A method of multi-loop patrolling configuration for high orbit satellite regional protection, characterized in that, The configuration method comprises the following steps: S1: According to the protection task, input the number n of protection objects in the high-orbit satellite regional protection, the initial phase distribution r of the orbit G And the safe escort distance Δr H The number m1 of the first layer of patrol satellites, and the number p of patrol rings S2: According to the number of patrol rings p, the safety escort distance Δr H , the number of first-layer patrol satellites m1, the number of satellites on the east and west drift orbits corresponding to each patrol ring, and the initial phase of the patrol satellites on the east and west drift orbits are calculated. S3: The safety escort distance Δr is calculated according to the safety escort distance Δr H The escort distance of the i-th layer is calculated The two pulse velocity increments of the ascending and descending processes of the patrol ring, and the orbital transfer time of the ascending and descending processes are calculated; S4: according to the calculated initial phase of the inspection satellite on the east and west orbit, the east and west orbit transfer time corresponding to each layer of the inspection ring is calculated, and the fuel consumption of each inspection satellite on the inspection ring is calculated; S5: according to the obtained parameters, a multi-ring inspection configuration for high-orbit satellite regional protection is established.

2. A multi-loop patrolling configuration method for high orbit satellite regional defense according to claim 1, characterized in that, The S1 comprises the following steps: According to the number n of protected objects, the track phase distribution The safe guard distance Δr H And the number p of the patrol ring layers, the geocentric polar coordinate system is established, wherein r i G The radius coordinate of the i th protected object in the polar coordinate is represented as r i, The angle coordinate of the i th protected object in the polar coordinate is represented as θ i, i = 1, 2…n; Write the n guard objects in the geocentric polar coordinate system According to the high orbit guard object distribution in the same radius orbit phase distribution r G on the orbit, so the formula 3. The multi-ring inspection configuration method for high-orbit satellite regional protection according to claim 1, characterized in that, S2.1: the inspection rings are numbered from inside to outside, the innermost layer is the first layer, and the outermost layer is the pth layer; S2.2: The safety escort distance Δr is determined according to the i-th layer patrol layer H The escort distance of the i-th layer patrol layer is determined as S2.3: Guard distance according to the i-th layer Calculate guard zone range; phase range of the i-th guard zone in the geocentric polar coordinate system Calculate guard zone range; phase range of the i-th guard zone in the geocentric polar coordinate system where the initial phase of the i-th tier of the patrol ring on the east drift orbit of the patrol satellite where the initial phase of the i-th tier of the patrol ring on the west drift orbit of the patrol satellite where the semi-major axis of the i-th tier of the patrol ring on the west drift orbit and the semi-major axis of the i-th tier of the patrol ring on the east drift orbit 4. The method of claim 1, wherein the high orbit satellite regional defense multi-loop patrol configuration method is characterized by, The S3 comprises the following steps: According to the number m1 of the first layer of inspection satellites, the number of inspection satellites on the east and west orbit of each layer of inspection ring is calculated; By increasing 1 layer of the patrol ring, the number of satellites on the layer is also increased by 1, and the number of satellites on the i-th layer of the patrol ring m is obtained i : m i = m1+i-1 (2) According to the number of patrol satellites m on the i-th layer patrol ring i And the patrol area phase range Carry out initial configuration design, and evenly distribute p i And q i Patrol satellites on the eastward and westward orbit of the i-th layer patrol ring, respectively The number of satellites p on the eastbound and westbound tracks in the i-th layer of the patrol ring is calculated i and q i ; wherein m i = p i + q i ; Calculate the p of the i-th layer on the eastbound orbit of the patrol ring i The initial polar coordinates of the patrol satellite are The initial polar coordinates of the i-th orbiting satellite from west to east on the i-th orbiting ring are According to the uniform distribution of phase angles, the initial phase of the i-th layer of the surveillance satellite on the east orbit of the surveillance ring is calculated is: The initial phase of the i-th layer of the inspection satellite on the inspection orbit of the west drift of the inspection ring is calculated is: Wherein, l represents the lth inspection satellite from west to east on the east orbit.

5. The multi-ring inspection configuration method for high-orbit satellite regional protection according to claim 1, characterized in that, the semi-major axis of the west drift orbit of the i-th tour the semi-major axis of the east drift orbit of the i-th tour the semi-major axis of the Hohmann transfer of the i-th tour i the two impulse velocity increments of the east rise of the i-th tour are calculated the two impulse velocity increments of the east rise of the i-th tour are calculated where μ = 3.986 x 10 14 m 3 s -2 = 3.986 x 10 5 km 3 s -2 , represents the gravitational constant of celestial bodies centered on the earth; Similarly, the two pulse velocity increments of the westward process of the i-th layer of the patrol ring may be calculated.

6. The multi-ring inspection configuration method for high-orbit satellite regional protection according to claim 5, characterized in that, calculating the orbital transfer time for the i-th layer for a westward pass and an eastward pass 7. The multi-ring inspection configuration method for high-orbit satellite regional protection according to claim 1, characterized in that, According to the phase, the longitude change of the east and west process of the ith layer of inspection ring is determined; According to the easterly drift process is by the western descending end to the eastern rising point During the orbit radius No change, Determining phase angle change is: Phase angle change of the i-th layer of the inspection ring west drift process 8. The multi-ring inspection configuration method for high-orbit satellite regional protection according to claim 7, characterized in that, According to the orbit angular velocity of the east and west process of the ith layer of inspection ring and the orbit height of the protected object respectively calculated, The relative angular velocity of the east and west process of the inspection satellite of the ith layer of inspection ring with respect to the protected object is calculated respectively The transfer time of the east and west process of the ith layer of inspection ring is calculated respectively according to the phase angle range of the east and west process of the ith layer of inspection ring and the relative angular velocity of the east and west process of the inspection satellite with respect to the protected object.

9. A method of multi-loop patrolling configuration for high orbit satellite regional protection according to claim 7, wherein, According to the eastward and westward transfer time in the i-th layer patrol ring and the eastward and westward drift time in the i-th layer patrol ring Calculate the patrol cycle T of the i-th layer patrol ring i c is: And according to the Hohmann transfer speed increment of the ith layer of inspection ring, the fuel consumption of each inspection satellite on the ith layer of inspection ring can be calculated.

Images